Progressive 3-axis multi-variable propulsion vectoring aerial and spacecraft vehicle

Abstract

The present embodiments and associated methods provide for a progressive 3-axis multi-variable propulsion vectoring aerial and spaceborne vehicle. One embodiment of the vehicle is comprised of top and side air intakes, a curved sphenoid air accumulator, a compressor section, a diffuser, a plurality of fuel burner cans, a turbine section, a gas plenum, top, side, and bottom exhaust ports, propellant burner cans, gas plenum iris, an onboard flight control computer, and top, side, and bottom exhaust port doors. Combustion gasses are produced which are directed by the gas plenum to the exhaust ports which provide thrust and lift to the vehicle. By selectively opening and closing the exhaust port doors, the vehicle may be made to rise, hover, and accelerate in any direction. Such an embodiment provides a vehicle that can directly ascend through the atmosphere into space.

What is claimed is:  
     
       1. A vehicle adapted for flight, comprising: 
       an airframe comprising a top, side, and bottom;  
       at least one top exhaust port on the airframe top;  
       at least one side exhaust port on the airframe side;  
       at least one bottom exhaust port on the airframe bottom, the top, side and bottom exhaust ports each comprising a door;  
       a gas plenum in fluid communication with the exhaust ports;  
       a gas plenum door;  
       at least one air intake located on the airframe, the at least one air intake comprising a door;  
       a fuel-burning gas-generating means adapted to produce gas, the fuel-burning gas-generating means in fluid communication with the at least one air intake; and  
       a propellant-burning gas-generating means adapted to produce gas, the propellant-burning gas-generating means in fluid communication with both the fuel-burning gas-generating means and the gas plenum, the gas plenum door disposed between the fuel-burning gas-generating means and the propellant-burning gas-generating means, the gas plenum door adapted to control the fluid communication between the fuel-burning gas-generating means and the propellant-burning gas-generating means, wherein the gas is distributed within the gas plenum to the exhaust ports, wherein the thrust required for horizontal and vertical flight is obtained by the controlled flow of the gas out of at least one exhaust port.  
     
     
       2. A vehicle adapted for flight according to  claim 1 , wherein the airframe is in the shape of a disk. 
     
     
       3. A vehicle adapted for flight according to  claim 1 , wherein the fuel-burning gas-generating means comprises: 
       an air accumulator in fluid communication with the at least one air intake;  
       a compressor section comprising a plurality of compressor blades, the compressor section in fluid communication with the air accumulator;  
       at least one fuel burner can in fluid communication with the compressor section;  
       a turbine section comprising a plurality of turbine blades, the turbine section in fluid communication with the fuel burner can, the turbine section in fluid communication with the propellant-burning gas-generating means; and  
       a fuel tank in fluid communication with the fuel burner can, wherein the gas is produced by igniting fuel in the fuel burner can.  
     
     
       4. A vehicle adapted for flight according to  claim 3 , wherein the fuel tank supplies jet fuel. 
     
     
       5. A vehicle adapted for flight according to  claim 1 , wherein the propellant-burning gas-generating means comprises: 
       at least one propellant burner can in fluid communication with the fuel-burning gas-generating means and with the gas plenum; and  
       a propellant tank in fluid communication with the at least one propellant burner can, wherein the gas is produced by igniting propellant in the propellant burner can.  
     
     
       6. A vehicle adapted for flight according to  claim 5 , wherein the propellant is hydrazine. 
     
     
       7. A vehicle adapted for flight according to  claim 5 , wherein the propellant is hydrogen and oxygen. 
     
     
       8. A vehicle adapted for flight according to  claim 1 , wherein the fuel-burning gas-generating means comprises: 
       an air accumulator in fluid communication with the at least one air in take;  
       a compressor section comprising a plurality of compressor blades, the compressor section in fluid communication with the air accumulator;  
       at least one fuel burner can in fluid communication with the compressor section;  
       a turbine section comprising a plurality of turbine blades, the turbine section in fluid communication with the fuel burner can, the gas plenum in fluid communication with the turbine section; and  
       a fuel tank in fluid communication with the at least one fuel burner can; and wherein the propellant-burning gas-generating means comprises:  
       a propellant tank; and  
       at least one propellant burner can in fluid communication with the propellant tank, the at least one propellant burner can in fluid communication with the gas plenum, the gas plenum door disposed between the turbine section and the gas plenum such that when closed the turbine section is substantially sealed off from the gas plenum.  
     
     
       9. A vehicle adapted for flight comprising: 
       an airframe comprising a top, side, and bottom;  
       at least one top exhaust port on the airframe top;  
       at least one side exhaust port on the airframe side;  
       at least one bottom exhaust port on the airframe bottom;  
       at least one air intake located on the airframe side, the airframe side being beveled at an angle down from horizontal;  
       a gas plenum in fluid communication with the exhaust ports;  
       the exhaust ports each comprising, a door;  
       a gas-generating means comprising:  
       an air accumulator in fluid communication with the at least one air intake;  
       a compressor section comprising a plurality of compressor blades, the compressor section in fluid communication with the air accumulator;  
       at least one fuel burner can in fluid communication with the compressor section;  
       a turbine section comprising a plurality of turbine blades, the turbine section in fluid communication with the fuel burner can, the gas plenum in fluid communication with the turbine section; and  
       a fuel tank in fluid communication with the at least one fuel burner can.  
     
     
       10. A vehicle adapted for flight comprising: 
       an airframe comprising a top, side, and bottom;  
       at least one top exhaust port on the airframe top;  
       at least one side exhaust port on the airframe side;  
       at least one bottom exhaust port on the airframe bottom;  
       the exhaust ports each comprising a door;  
       a gas plenum in fluid communication with the exhaust ports;  
       a gas-generating means comprising:  
       a propellant tank; and  
       at least one propellant burner can in fluid communication with the propellant tank, the at least one propellant burner can in fluid communication with the gas plenum.  
     
     
       11. A vehicle adapted for flight according to  claim 1 , wherein the airframe further comprises a progressive G-force alignment platform. 
     
     
       12. A vehicle adapted for flight according to  claim 1 , wherein the airframe comprises an oval shape. 
     
     
       13. A vehicle adapted for flight according to  claim 1 , wherein the airframe has landing gear. 
     
     
       14. A vehicle adapted for flight according to  claim 8 , wherein the fuel is jet fuel and the propellant comprises hydrazine. 
     
     
       15. A vehicle adapted for flight according to  claim 9 , wherein the fuel is jet fuel. 
     
     
       16. A vehicle adapted for flight according to  claim 5 , wherein the propellant comprises fuel and oxidizer. 
     
     
       17. A vehicle adapted for flight according to  claim 5 , wherein the propellant is hydrazine. 
     
     
       18. A method for controlling a vehicle adapted for flight, the vehicle comprising: 
       a flight control computer comprising a database of preprogrammed control parameters;  
       at least one vehicle position sensor in electrical communication with the flight control computer;  
       an airframe comprising:  
       a top, side, and bottom; and  
       at least one top exhaust port on the airframe top, at least one side exhaust port on the airframe side, and at least one bottom exhaust port on the airframe bottom, the exhaust ports each comprising a door; and  
       a supply of gas distributed to the at least one top, side and bottom exhaust port, wherein the thrust required for horizontal and vertical flight is obtained by the controlled flow of gas out of one or more exhaust ports, the flight control computer in electrical communication with the exhaust port doors;  
       the method comprising:  
       communicating a course change command to the flight control computer wherein the flight control computer chooses from the database of preprogrammed control parameters based on the course change command to affect the course change by selectively opening and closing at least one exhaust port door;  
       sensing the vehicle position with the at least one position sensor;  
       communicating the position data to the flight control computer; and  
       processing the position data with the flight control computer such that the flight control computer may choose the appropriate preprogrammed control parameters to affect the course change, wherein the fight control computer and the at least one position sensor are in a continual feed-back loop.  
     
     
       19. A vehicle adapted for flight, comprising: 
       an airframe comprising a top, side, and bottom;  
       at least one top exhaust port on the airframe top;  
       at least one side exhaust port on the airframe side;  
       at least one bottom exhaust port on the airframe bottom;  
       a supply of gas distributed within the airframe to the at least one top, side and bottom exhaust ports, wherein the thrust required for horizontal and vertical flight is obtained by the controlled flow of gas out of at least one exhaust port;  
       at least one air intake located on the airframe, the at least one air intake comprising a door;  
       each exhaust port having an exhaust port door;  
       an air accumulator in fluid communication with the at least one air intake;  
       a gas-generating means within the airframe comprising:  
       a compressor section comprising a plurality of compressor blades, the compressor section in fluid communication with the air accumulator;  
       at least one fuel burner can in fluid communication with the compressor section;  
       a turbine section comprising a plurality of turbine blades, the turbine section in fluid communication with the burner can;  
       a gas plenum in fluid communication with the turbine section, the exhaust ports in fluid communication with the gas plenum;  
       a fuel tank in fluid communication with the at least one fuel burner can;  
       a propellant tank;  
       at least one propellant burner can in fluid communication with the propellant tank, the at least one propellant burner can in fluid communication with the gas plenum;  
       a gas plenum door between the turbine section and the gas plenum such that when closed the turbine section is substantially scaled off from the gas plenum; and  
       an onboard flight control computer, such that the flight control computer controls the opening of the exhaust port doors.  
     
     
       20. A vehicle adapted for flight according to  claim 1 , wherein the airframe side is beveled at an angle down from horizontal, at least one of the air intakes located on the airframe side. 
     
     
       21. A vehicle adapted for flight according to  claim 1 , wherein the at least one top, side and bottom exhaust port doors are adapted to be operated independently, in any combination with each other, and in any range between fully open and fully closed. 
     
     
       22. A vehicle adapted for flight according to  claim 3 , further comprising at least one exhaust port preferentially placed at a cant angle in an opposing direction to a gyroscopic effect. 
     
     
       23. A vehicle adapted for flight according to  claim 9 , wherein the at least one top, side and bottom exhaust port doors are adapted to be operated independently, in any combination with each other, and in any range between fully open and fully closed. 
     
     
       24. A vehicle adapted for flight according to  claim 19 , wherein the airframe side is beveled at an angle down from horizontal, at least one of the air intakes located on the airframe side. 
     
     
       25. A vehicle adapted for flight according to  claim 19 , wherein the at least one top, side and bottom exhaust port doors are adapted to be operated independently, in any combination with each other, and in any range between fully open and fully closed. 
     
     
       26. A vehicle adapted for flight according to  claim 19 , wherein the airframe is in the shape of a disk. 
     
     
       27. A vehicle adapted for flight according to  claim 19 , wherein the fuel tank supplies jet fuel. 
     
     
       28. A vehicle adapted for flight according to  claim 19 , wherein the propellant comprises fuel and oxidizer. 
     
     
       29. A vehicle adapted for flight according to  claim 19 , further comprising at least one exhaust port preferentially placed at a cant angle in an opposing direction to a gyroscopic effect. 
     
     
       30. A vehicle adapted for flight according to  claim 19 , wherein the airframe further comprises a progressive G-force alignment platform. 
     
     
       31. A vehicle adapted for flight according to  claim 19 , further comprising: 
       a flight control computer comprising a database of preprogrammed control parameters; and  
       at least one vehicle position sensor in electrical communication with the flight control computer, the position sensor adapted to communicate position data to the flight control computer, the fight control computer and the at least one position sensor in a continual feed-back loop, the flight control computer adapted to accept a course change command and choose from the database the appropriate preprogrammed control parameters based on the course change command to affect the course change by selectively opening and closing at least one exhaust port door.  
     
     
       32. A vehicle adapted for flight, comprising: 
       an airframe comprising a plurality of exhaust ports on a top, a plurality of exhaust ports on a side, and a plurality of exhaust ports on a bottom;  
       at least one of said exhaust ports on each of the airframe top, side and bottom, said exhaust ports each comprising a door adapted to be operated independently, in any combination with each other, and in any range between fully open and fully closed; and  
       a supply of gas distributed to the exhaust ports, wherein the thrust required for horizontal and vertical flight is obtained by the controlled flow of the gas out of the exhaust ports.  
     
     
       33. A vehicle adapted for flight according to  claim 32 , further comprising: 
       a gas plenum, the gas plenum in fluid communication with the exhaust ports;  
       a gas plenum door;  
       at least one air intake located on the airframe, the at least one air intake comprising a door;  
       a fuel-burning gas-generating means adapted to produce gas, the fuel-burning gas-generating means in fluid communication with the at least one air intake; and  
       a propellant-burning gas-generating means adapted to produce gas, the propellant-burning gas-generating means in fluid communication with both the fuel-burning gas-generating means and the gas plenum, the gas plenum door disposed between the fuel-burning gas-generating means and the propellant-burning gas-generating means, the gas plenum door adapted to control the fluid communication between the fuel-burning gas-generating means and the propellant-burning gas-generating means.  
     
     
       34. A vehicle adapted for flight according to  claim 32 , wherein the airframe side is beveled towards the airframe bottom, at least one of the air intakes is located on the airframe side and points at an angle down from horizontal. 
     
     
       35. A vehicle adapted for flight according to  claim 32 , further comprising: 
       a gas plenum in fluid communication with the exhaust ports, wherein the gas-generating means comprises:  
       a propellant tank; and  
       at least one propellant burner can in fluid communication with the propellant tank and the gas plenum.  
     
     
       36. A vehicle adapted for flight according to  claim 32 , further comprising: 
       at least one air intake located on the airframe;  
       an air accumulator in fluid communication with the at least one air intake;  
       a gas plenum in fluid communication with the exhaust ports;  
       the gas-generating means comprising:  
       a compressor section comprising a plurality of compressor blades, the compressor section in fluid communication with the air accumulator;  
       at least one fuel burner can in fluid communication with the compressor section;  
       a turbine section comprising a plurality of turbine blades, the turbine section in fluid communication with the fuel burner can and the gas plenum; and  
       a fuel tank in fluid communication with the at least one fuel burner can.  
     
     
       37. A vehicle adapted for flight according to  claim 36 , wherein the airframe side is beveled towards the airframe bottom, at least one of the air intakes is located on the airframe side and points at an angle down from horizontal.